US20090255267A1 - Comubstor seal having multiple cooling fluid pathways - Google Patents
Comubstor seal having multiple cooling fluid pathways Download PDFInfo
- Publication number
- US20090255267A1 US20090255267A1 US12/100,679 US10067908A US2009255267A1 US 20090255267 A1 US20090255267 A1 US 20090255267A1 US 10067908 A US10067908 A US 10067908A US 2009255267 A1 US2009255267 A1 US 2009255267A1
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- Prior art keywords
- combustor
- seal
- component
- cooling
- pathway
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Definitions
- the subject invention relates to combustors. More particularly, the subject invention relates to sealing between combustor components.
- Air management is an important consideration in combustor design. Air streams provide an oxidizer for a combustion process and also provide cooling to hot components of the combustor. Seals are typically provided between various components of the combustor to prevent hot combustion gas from leaking from the combustor. Seal configurations and functions are unique in a combustor. A seal providing complete sealing of flow from one area to another may not be desired, but rather a seal resulting in a small amount of cooling air “leak” may be preferred. Within combustion zones, cooling must be properly designed to provide adequate cooling for components while only minimally disturbing combustion ignition and stability. Cooling air streams “leaked” through the seal may also be directed to reducing thermal-acoustic oscillation of the combustor.
- seals typically include C-Rings, fingered hula rings, cloth seals, and the like, and are subjected to high temperature and pressure as well as high gradients of pressure and temperature across the seals.
- Current seals can be further improved for provision of cooling flow to overcome excessive leakage around the seal at various levels of temperature and/or pressure and during temperature and/or pressure transitions, and/or wear of the seal.
- a combustor for a gas turbine includes a first combustor component and a second combustor component.
- the second combustor component is at least partially insertable into the first combustor component, and the first combustor component and second combustor component define a combustion fluid pathway.
- a combustor seal is located between the first combustor component and the second combustor component.
- the combustor seal defines at least one inner cooling pathway between the combustor seal and the second combustor component and at least one outer cooling pathway between the combustor seal and the first combustor component for cooling the first combustor component and second combustor component.
- a method for cooling a first combustor component and a second combustor component includes locating a combustor seal radially between the first combustor component and the second combustor component. Cooling fluid flows through at least one inner cooling pathway defined by the combustor seal and the second combustor component. Cooling fluid also flows through at least one outer cooling pathway defined by the combustor seal and the second combustor component. The spent cooling fluid then flows into the combustion fluid.
- FIG. 1 is a schematic cross-sectional view of a gas turbine
- FIG. 2 is a cross-sectional view of a portion of a combustor of the gas turbine of FIG. 1 including an embodiment of a combustor seal;
- FIG. 3 is a partially exploded view of the combustor seal of FIG. 2 ;
- FIG. 4 is a cross-sectional view of an embodiment of a reversed seal of FIG. 2 ;
- FIG. 5 is a cross-sectional view of an embodiment of a combustor seal including a coil
- FIG. 6 is a plane view of the combustor seal of FIG. 5 ;
- FIG. 7 is a cross-sectional view of yet another embodiment of a combustor seal
- FIG. 8 is a plane view of the combustor seal of FIG. 7 ;
- FIG. 9 is a cross-sectional view of an embodiment of a combustor seal having multiple wave sections
- FIG. 10 is a plane view of the combustor seal of FIG. 9 ;
- FIG. 11 is a cross-sectional view of a combustor seal having a mesh configuration
- FIG. 12 is a plane view of the combustor seal of FIG. 11 .
- the gas turbine 10 includes a compressor 12 which provides compressed fluid to a combustor 14 . Fuel is injected into the combustor 14 , mixes with the compressed air and is ignited. The hot gas products of the combustion flow to a turbine 16 which extracts work from the hot gas to drive a rotor shaft 18 which in turn drives the compressor 12 .
- a transition piece 20 is coupled at an upstream end 22 to the combustor 14 at a combustor liner 24 and at a downstream end 26 to an aft frame 28 of the turbine 16 . The transition piece 20 carries hot gas flow from the combustor liner 24 to the turbine 16 .
- the combustor 14 includes a combustor sleeve 30 spaced radially outward from the combustor liner 24 defining a combustor flow channel 32 therebetween.
- a combustor cap 34 is coupled to an upstream end 36 of the combustor liner 24 and includes at least one nozzle 38 disposed therein an extending into a combustion chamber 40 defined by the combustor cap 34 and the combustor liner 24 .
- An impingement sleeve 42 is coupled to the combustor sleeve 30 and is radially spaced from the transition piece 20 defining a transition flow channel 44 therebetween.
- discharge flow 46 flows from the compressor 12 through a diffuser 48 to the impingement sleeve 42 .
- the discharge flow 46 proceeds through a plurality of impingement holes 50 in the impingement sleeve 42 and toward the combustor 14 in the transition flow channel 44 .
- the discharge flow 46 proceeds from the transition flow channel 44 and through the combustor flow channel 32 until it is finally introduced to the combustor liner 24 through the at least one nozzle 38 .
- the relatively cool discharge flow 46 further provides much needed cooling to the components exposed to hot combustion gas, for example, the combustor liner 24 and the transition piece 20 .
- interfaces between adjacent components exposed to hot combustion gases are configured as lap joints 56 wherein, for example, a downstream end 58 of the combustor liner 24 is configured to be insertable into the upstream end 22 of the transition piece 20 .
- a seal 60 is disposed radially between the overlapping portions of the transition piece 20 and the combustor liner 24 and extends perimetrically around the joint 56 .
- Another example of such an application is one in which the seal 60 disposed between overlapping portions of the combustor liner 24 and the combustor cap 34 .
- the seal 60 is disposed between overlapping portions of the combustor cap 34 and the at least one nozzle 38 .
- the seal 60 of is configured with a wave-shaped cross section and includes two layers, an outer seal 62 and an inner seal 64 .
- the seal 60 includes at least one support 66 comprising, for example, a weld, which secures the seal 60 to at least one of the transition piece 20 or the combustor liner 24 .
- the inner seal 64 includes at least one inner seal slot 68 disposed at an upstream inner seal end 70 and open at the upstream inner seal end 70 .
- the inner seal 64 further includes at least one inner seal slot 68 disposed at a downstream inner seal end 72 and open at the downstream inner seal end 72 .
- the at least one inner seal slot 68 may include one or more scallops 74 to reduce stress in the inner seal 64 at the inner seal slot 68 .
- the outer seal 62 includes a plurality of impingement holes 76 disposed at an upstream outer seal end 78 . At least one of the impingement holes 76 is located over at least one inner seal slot 68 .
- a wave section 80 of the outer seal 62 includes at least one wave slot 82 which may include one or more scallops 74 to reduce stress in the outer seal 62 at the wave slot 82 .
- the seal 60 is disposed between transition piece 20 and the combustor liner 24 such that the inner seal 64 contacts the combustor liner 24 at the upstream inner seal end 70 and the downstream inner seal end 72 .
- the outer seal 62 contacts the transition piece 20 at the wave section 80 .
- a first portion 84 of the flow proceeds through the at least one wave slot 82 thereby providing cooling to the transition piece 20
- a second portion 86 of the flow through the inner seal slots 68 and/or the impingement holes 76 thereby providing cooling to the combustor liner 24 .
- FIG. 3 has two seal layers, configurations having different numbers of seal layers, for example, one layer or three layers, are contemplated within the scope of the present disclosure.
- the seal 60 of FIG. 2 may be reversed or flipped such that the upstream inner seal end 70 and the downstream inner seal end 72 contact the transition piece 20 , and the seal 60 contacts the combustor liner 24 at the wave section 80 . Reversal of the seal 60 as shown in FIG. 4 can enhance cooling of the combustor liner 24 such that other cooling flows to the combustor liner 24 can be reduced or eliminated.
- the seal 60 is fixed to the transition piece 20 so thermal expansion and/or installation displacement of the transition piece 20 will not affect the performance of the seal 60 .
- the seal 60 comprises a coil 88 disposed radially between the transition piece 20 and the combustor liner 24 and contacting both the transition piece 20 and combustor liner 24 .
- the coil 88 extends perimetrically around the joint 56 and is secured to at least one of the transition piece 20 or the combustor liner 24 by at least one support 66 .
- a sleeve 90 which is shown with annular cross-section, is located inside the coil 88 .
- the coil 88 and the sleeve 90 are configured to allow the flow to proceed between coil windings 92 as shown in FIG. 6 . Referring again to FIG.
- the first portion 84 proceeds between coil windings 92 to provide cooling to the transition piece 20
- the second portion 86 proceeds between coil windings 92 to provide cooling to the combustor liner 24
- the sleeve 90 provides sealing to prevent undesired outflow of hot gas from the transition piece 20 .
- the seal 60 comprises a solid or tubular rod 94 disposed radially between the transition piece 20 and the combustor liner 24 and contacting both the transition piece 20 and the combustor liner 24 .
- the rod 94 extends perimetrically around the joint 56 and is secured to at least one of the transition piece 20 or the combustor liner 24 by at least one support 66 .
- a plurality of cooling slots 96 are disposed in the rod 94 as shown in FIG. 8 to provide cooling flow to the transition piece 20 and the combustor liner 24 .
- the cooling slots 96 shown in FIG. 8 are disposed substantially axially in the rod 94 , but it is to be appreciated that cooling slots 96 disposed in other angular directions are contemplated within the scope of the present disclosure.
- FIG. 9 Another alternative embodiment of a seal 60 is illustrated in FIG. 9 .
- the seal 60 comprises at least one seal layer 98 having a upstream seal end 100 , a seal downstream end 102 , and a plurality of wave sections 104 disposed therebetween.
- the seal layer 98 extends perimetrically around the joint 56 and is secured to at least one of the transition piece 20 or the combustor liner 24 by at least one support 66 and includes at least one end slot 106 disposed at each seal end 100 , 102 .
- Each wave section 104 contacts one of the transition piece 20 or the combustor liner 24 and includes at least one wave slot 82 as shown in FIG. 10 .
- the at least one wave slot 82 may include one or more scallops 74 to reduce stress in the seal layer 98 at the wave slot 82 .
- the first portion 84 proceeds through the wave slots 82 to provide cooling to the transition piece 20
- the second portion 86 proceeds through the end slots 106 disposed at the seal upstream end 100 , through the wave slots 82 and through the end slots 106 disposed at the seal downstream end 102 to provide cooling to the combustor liner 24 .
- the embodiment shown in FIG. 9 includes three wave sections 104 , and seal ends 100 , 102 which contact the combustor liner 24 , other quantities of wave sections 104 and other orientations of seal ends 100 , 102 are contemplated by the present disclosure.
- FIG. 11 Yet another embodiment of a seal 60 is illustrated in FIG. 11 .
- the seal 60 of this embodiment comprises a multi-layer mesh.
- the mesh in FIG. 11 has an inner mesh layer 108 and an outer mesh layer 110 .
- the inner mesh layer 108 is formed from a plurality of, for example, inner wires 112 arranged to define a plurality of inner mesh channels 114 .
- the outer mesh layer 110 is formed from a plurality of, for example, outer wires 116 arranged to define a plurality of outer mesh channels 118 .
- the inner mesh layer 108 and the outer mesh layer 110 are configured such that a channel angle 120 exists between the inner mesh channels 114 and the outer mesh channels 118 .
- the first portion 84 proceeds through the outer mesh channels 118 to provide cooling to the transition piece 20
- the second portion 86 proceeds through the inner mesh channels 114 to provide cooling to the combustor liner 24 .
- seals 60 disposed between a transition piece 20 and a combustor liner 24
- the seal 60 can be utilized at other locations in the combustor 14 or gas turbine 10 , for example, between the transition piece 20 and the aft frame 28 or between the combustor liner 24 and the combustor cap 34 .
Abstract
Description
- The subject invention relates to combustors. More particularly, the subject invention relates to sealing between combustor components.
- Air management is an important consideration in combustor design. Air streams provide an oxidizer for a combustion process and also provide cooling to hot components of the combustor. Seals are typically provided between various components of the combustor to prevent hot combustion gas from leaking from the combustor. Seal configurations and functions are unique in a combustor. A seal providing complete sealing of flow from one area to another may not be desired, but rather a seal resulting in a small amount of cooling air “leak” may be preferred. Within combustion zones, cooling must be properly designed to provide adequate cooling for components while only minimally disturbing combustion ignition and stability. Cooling air streams “leaked” through the seal may also be directed to reducing thermal-acoustic oscillation of the combustor.
- These seals typically include C-Rings, fingered hula rings, cloth seals, and the like, and are subjected to high temperature and pressure as well as high gradients of pressure and temperature across the seals. Current seals can be further improved for provision of cooling flow to overcome excessive leakage around the seal at various levels of temperature and/or pressure and during temperature and/or pressure transitions, and/or wear of the seal.
- A combustor for a gas turbine includes a first combustor component and a second combustor component. The second combustor component is at least partially insertable into the first combustor component, and the first combustor component and second combustor component define a combustion fluid pathway. A combustor seal is located between the first combustor component and the second combustor component. The combustor seal defines at least one inner cooling pathway between the combustor seal and the second combustor component and at least one outer cooling pathway between the combustor seal and the first combustor component for cooling the first combustor component and second combustor component.
- A method for cooling a first combustor component and a second combustor component includes locating a combustor seal radially between the first combustor component and the second combustor component. Cooling fluid flows through at least one inner cooling pathway defined by the combustor seal and the second combustor component. Cooling fluid also flows through at least one outer cooling pathway defined by the combustor seal and the second combustor component. The spent cooling fluid then flows into the combustion fluid.
- These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
- The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other objects, features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
-
FIG. 1 is a schematic cross-sectional view of a gas turbine; -
FIG. 2 is a cross-sectional view of a portion of a combustor of the gas turbine ofFIG. 1 including an embodiment of a combustor seal; -
FIG. 3 is a partially exploded view of the combustor seal ofFIG. 2 ; -
FIG. 4 is a cross-sectional view of an embodiment of a reversed seal ofFIG. 2 ; -
FIG. 5 is a cross-sectional view of an embodiment of a combustor seal including a coil; -
FIG. 6 is a plane view of the combustor seal ofFIG. 5 ; -
FIG. 7 is a cross-sectional view of yet another embodiment of a combustor seal; -
FIG. 8 is a plane view of the combustor seal ofFIG. 7 ; -
FIG. 9 is a cross-sectional view of an embodiment of a combustor seal having multiple wave sections; -
FIG. 10 is a plane view of the combustor seal ofFIG. 9 ; -
FIG. 11 is a cross-sectional view of a combustor seal having a mesh configuration; and -
FIG. 12 is a plane view of the combustor seal ofFIG. 11 . - The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
- Shown in
FIG. 1 is agas turbine 10. Thegas turbine 10 includes acompressor 12 which provides compressed fluid to acombustor 14. Fuel is injected into thecombustor 14, mixes with the compressed air and is ignited. The hot gas products of the combustion flow to aturbine 16 which extracts work from the hot gas to drive arotor shaft 18 which in turn drives thecompressor 12. Atransition piece 20 is coupled at anupstream end 22 to thecombustor 14 at acombustor liner 24 and at adownstream end 26 to anaft frame 28 of theturbine 16. Thetransition piece 20 carries hot gas flow from thecombustor liner 24 to theturbine 16. Thecombustor 14 includes acombustor sleeve 30 spaced radially outward from thecombustor liner 24 defining acombustor flow channel 32 therebetween. Acombustor cap 34 is coupled to anupstream end 36 of thecombustor liner 24 and includes at least onenozzle 38 disposed therein an extending into acombustion chamber 40 defined by thecombustor cap 34 and thecombustor liner 24. Animpingement sleeve 42 is coupled to thecombustor sleeve 30 and is radially spaced from thetransition piece 20 defining atransition flow channel 44 therebetween. - During operation,
discharge flow 46 flows from thecompressor 12 through adiffuser 48 to theimpingement sleeve 42. Thedischarge flow 46 proceeds through a plurality ofimpingement holes 50 in theimpingement sleeve 42 and toward thecombustor 14 in thetransition flow channel 44. Thedischarge flow 46 proceeds from thetransition flow channel 44 and through thecombustor flow channel 32 until it is finally introduced to thecombustor liner 24 through the at least onenozzle 38. In addition to providing air to thecombustor 14 for the combustion process, the relativelycool discharge flow 46 further provides much needed cooling to the components exposed to hot combustion gas, for example, thecombustor liner 24 and thetransition piece 20. - As shown in
FIG. 2 , interfaces between adjacent components exposed to hot combustion gases, for example, thetransition piece 20 and thecombustor liner 24, are configured aslap joints 56 wherein, for example, adownstream end 58 of thecombustor liner 24 is configured to be insertable into theupstream end 22 of thetransition piece 20. Aseal 60 is disposed radially between the overlapping portions of thetransition piece 20 and thecombustor liner 24 and extends perimetrically around thejoint 56. Another example of such an application is one in which theseal 60 disposed between overlapping portions of thecombustor liner 24 and thecombustor cap 34. Yet another example of such application is one in which theseal 60 is disposed between overlapping portions of thecombustor cap 34 and the at least onenozzle 38. In one embodiment, theseal 60 of is configured with a wave-shaped cross section and includes two layers, anouter seal 62 and aninner seal 64. In some embodiments, theseal 60 includes at least onesupport 66 comprising, for example, a weld, which secures theseal 60 to at least one of thetransition piece 20 or thecombustor liner 24. - Referring now to
FIG. 3 , theinner seal 64 includes at least oneinner seal slot 68 disposed at an upstreaminner seal end 70 and open at the upstreaminner seal end 70. Theinner seal 64 further includes at least oneinner seal slot 68 disposed at a downstreaminner seal end 72 and open at the downstreaminner seal end 72. The at least oneinner seal slot 68 may include one ormore scallops 74 to reduce stress in theinner seal 64 at theinner seal slot 68. Theouter seal 62 includes a plurality ofimpingement holes 76 disposed at an upstreamouter seal end 78. At least one of theimpingement holes 76 is located over at least oneinner seal slot 68. Awave section 80 of theouter seal 62 includes at least onewave slot 82 which may include one ormore scallops 74 to reduce stress in theouter seal 62 at thewave slot 82. - Referring now to
FIG. 2 , theseal 60 is disposed betweentransition piece 20 and thecombustor liner 24 such that theinner seal 64 contacts thecombustor liner 24 at the upstreaminner seal end 70 and the downstreaminner seal end 72. Theouter seal 62 contacts thetransition piece 20 at thewave section 80. In operation, a portion of the flow through thetransition flow channel 44 flows past anupstream end 22 of thetransition piece 20 and between thetransition piece 20 andcombustor liner 24. Afirst portion 84 of the flow proceeds through the at least onewave slot 82 thereby providing cooling to thetransition piece 20, and asecond portion 86 of the flow through theinner seal slots 68 and/or the impingement holes 76 thereby providing cooling to thecombustor liner 24. While the embodiment ofFIG. 3 has two seal layers, configurations having different numbers of seal layers, for example, one layer or three layers, are contemplated within the scope of the present disclosure. - In an embodiment as shown in
FIG. 4 , theseal 60 ofFIG. 2 may be reversed or flipped such that the upstreaminner seal end 70 and the downstreaminner seal end 72 contact thetransition piece 20, and theseal 60 contacts thecombustor liner 24 at thewave section 80. Reversal of theseal 60 as shown inFIG. 4 can enhance cooling of thecombustor liner 24 such that other cooling flows to thecombustor liner 24 can be reduced or eliminated. In this embodiment, theseal 60 is fixed to thetransition piece 20 so thermal expansion and/or installation displacement of thetransition piece 20 will not affect the performance of theseal 60. - In another embodiment as shown in
FIG. 5 , theseal 60 comprises acoil 88 disposed radially between thetransition piece 20 and thecombustor liner 24 and contacting both thetransition piece 20 andcombustor liner 24. Thecoil 88 extends perimetrically around the joint 56 and is secured to at least one of thetransition piece 20 or thecombustor liner 24 by at least onesupport 66. Asleeve 90, which is shown with annular cross-section, is located inside thecoil 88. Thecoil 88 and thesleeve 90 are configured to allow the flow to proceed betweencoil windings 92 as shown inFIG. 6 . Referring again toFIG. 5 , thefirst portion 84 proceeds betweencoil windings 92 to provide cooling to thetransition piece 20, and thesecond portion 86 proceeds betweencoil windings 92 to provide cooling to thecombustor liner 24, while thesleeve 90 provides sealing to prevent undesired outflow of hot gas from thetransition piece 20. - In another embodiment shown in
FIG. 7 , theseal 60 comprises a solid ortubular rod 94 disposed radially between thetransition piece 20 and thecombustor liner 24 and contacting both thetransition piece 20 and thecombustor liner 24. Therod 94 extends perimetrically around the joint 56 and is secured to at least one of thetransition piece 20 or thecombustor liner 24 by at least onesupport 66. A plurality of coolingslots 96 are disposed in therod 94 as shown inFIG. 8 to provide cooling flow to thetransition piece 20 and thecombustor liner 24. The coolingslots 96 shown inFIG. 8 are disposed substantially axially in therod 94, but it is to be appreciated that coolingslots 96 disposed in other angular directions are contemplated within the scope of the present disclosure. - Another alternative embodiment of a
seal 60 is illustrated inFIG. 9 . Theseal 60 comprises at least oneseal layer 98 having aupstream seal end 100, a sealdownstream end 102, and a plurality ofwave sections 104 disposed therebetween. Theseal layer 98 extends perimetrically around the joint 56 and is secured to at least one of thetransition piece 20 or thecombustor liner 24 by at least onesupport 66 and includes at least oneend slot 106 disposed at eachseal end wave section 104 contacts one of thetransition piece 20 or thecombustor liner 24 and includes at least onewave slot 82 as shown inFIG. 10 . The at least onewave slot 82 may include one ormore scallops 74 to reduce stress in theseal layer 98 at thewave slot 82. Referring again toFIG. 9 , thefirst portion 84 proceeds through thewave slots 82 to provide cooling to thetransition piece 20, and thesecond portion 86 proceeds through theend slots 106 disposed at the sealupstream end 100, through thewave slots 82 and through theend slots 106 disposed at the sealdownstream end 102 to provide cooling to thecombustor liner 24. While the embodiment shown inFIG. 9 includes threewave sections 104, and seal ends 100, 102 which contact thecombustor liner 24, other quantities ofwave sections 104 and other orientations of seal ends 100, 102 are contemplated by the present disclosure. - Yet another embodiment of a
seal 60 is illustrated inFIG. 11 . Theseal 60 of this embodiment comprises a multi-layer mesh. The mesh inFIG. 11 has an inner mesh layer 108 and an outer mesh layer 110. The inner mesh layer 108 is formed from a plurality of, for example,inner wires 112 arranged to define a plurality ofinner mesh channels 114. Similarly, the outer mesh layer 110 is formed from a plurality of, for example,outer wires 116 arranged to define a plurality ofouter mesh channels 118. As shown inFIG. 12 , the inner mesh layer 108 and the outer mesh layer 110 are configured such that a channel angle 120 exists between theinner mesh channels 114 and theouter mesh channels 118. The channel angle 120 ofFIG. 12 is substantially 90 degrees, but it is to be appreciated that other channel angles 120 are contemplated depending on desired cooling effects. To provide cooling, thefirst portion 84 proceeds through theouter mesh channels 118 to provide cooling to thetransition piece 20, and thesecond portion 86 proceeds through theinner mesh channels 114 to provide cooling to thecombustor liner 24. - While the embodiments above describe
seals 60 disposed between atransition piece 20 and acombustor liner 24, theseal 60 can be utilized at other locations in thecombustor 14 orgas turbine 10, for example, between thetransition piece 20 and theaft frame 28 or between thecombustor liner 24 and thecombustor cap 34. - While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims (19)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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US12/100,679 US7594401B1 (en) | 2008-04-10 | 2008-04-10 | Combustor seal having multiple cooling fluid pathways |
DE102009003770A DE102009003770A1 (en) | 2008-04-10 | 2009-04-08 | Combustor gasket with several cooling fluid passages |
JP2009093512A JP2009250242A (en) | 2008-04-10 | 2009-04-08 | Combustor seal having multiple cooling fluid pathways |
FR0952349A FR2929992A1 (en) | 2008-04-10 | 2009-04-09 | COMBUSTION SYSTEM WITH MULTI-PIPE SEAL OF COOLING FLUID |
CN200910132772XA CN101556042B (en) | 2008-04-10 | 2009-04-10 | Combustor seal having multiple cooling fluid pathways |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US12/100,679 US7594401B1 (en) | 2008-04-10 | 2008-04-10 | Combustor seal having multiple cooling fluid pathways |
Publications (2)
Publication Number | Publication Date |
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US7594401B1 US7594401B1 (en) | 2009-09-29 |
US20090255267A1 true US20090255267A1 (en) | 2009-10-15 |
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US12/100,679 Expired - Fee Related US7594401B1 (en) | 2008-04-10 | 2008-04-10 | Combustor seal having multiple cooling fluid pathways |
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US (1) | US7594401B1 (en) |
JP (1) | JP2009250242A (en) |
CN (1) | CN101556042B (en) |
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FR (1) | FR2929992A1 (en) |
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US10041675B2 (en) * | 2014-06-04 | 2018-08-07 | Pratt & Whitney Canada Corp. | Multiple ventilated rails for sealing of combustor heat shields |
KR102038112B1 (en) * | 2017-10-13 | 2019-10-29 | 두산중공업 주식회사 | Combustor and gas turbine including the same |
US20220390114A1 (en) * | 2021-06-07 | 2022-12-08 | General Electric Company | Combustor for a gas turbine engine |
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US20100077761A1 (en) * | 2008-09-30 | 2010-04-01 | General Electric Company | Impingement cooled combustor seal |
US8079219B2 (en) * | 2008-09-30 | 2011-12-20 | General Electric Company | Impingement cooled combustor seal |
US20160252249A1 (en) * | 2013-10-07 | 2016-09-01 | United Technologies Corporation | Combustor wall with tapered cooling cavity |
US10047958B2 (en) * | 2013-10-07 | 2018-08-14 | United Technologies Corporation | Combustor wall with tapered cooling cavity |
WO2016204534A1 (en) * | 2015-06-16 | 2016-12-22 | 두산중공업 주식회사 | Combustion duct assembly for gas turbine |
US10782024B2 (en) | 2015-06-16 | 2020-09-22 | DOOSAN Heavy Industries Construction Co., LTD | Combustion duct assembly for gas turbine |
Also Published As
Publication number | Publication date |
---|---|
DE102009003770A1 (en) | 2009-10-15 |
US7594401B1 (en) | 2009-09-29 |
FR2929992A1 (en) | 2009-10-16 |
CN101556042B (en) | 2013-05-22 |
CN101556042A (en) | 2009-10-14 |
JP2009250242A (en) | 2009-10-29 |
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